CN112678192B - Unmanned aerial vehicle with convertible flight posture - Google Patents
Unmanned aerial vehicle with convertible flight posture Download PDFInfo
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- CN112678192B CN112678192B CN202110022100.4A CN202110022100A CN112678192B CN 112678192 B CN112678192 B CN 112678192B CN 202110022100 A CN202110022100 A CN 202110022100A CN 112678192 B CN112678192 B CN 112678192B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention provides an unmanned aerial vehicle with a convertible flight posture, which relates to the technical field of unmanned aerial vehicles and aims at solving the problems that an original unmanned aerial vehicle is not provided with a parachute and a structural device with a damping function for buffering landing, so that the phenomenon that the unmanned aerial vehicle falls carelessly to hit passers-by easily occurs, and when the unmanned aerial vehicle falls on the ground, the falling gravity of the unmanned aerial vehicle cannot be buffered, the unmanned aerial vehicle cannot be ensured to keep basic structural integrity after falling, and meanwhile, the practicability of the unmanned aerial vehicle is reduced; the machine body is of a cuboid structure, and a hollow irregular cylinder-shaped ejection box is fixedly arranged at the upper end of the middle of the machine body. According to the invention, the fixing rod is fixedly arranged above the unmanned aerial vehicle, so that the unmanned aerial vehicle is prevented from being out of control and falling down and carelessly hitting a passerby, the main part of the unmanned aerial vehicle body can be prevented from being broken when the unmanned aerial vehicle falls down, the unmanned aerial vehicle device is timely protected, the loss is ensured to be minimized, and meanwhile, the safety practical function of the unmanned aerial vehicle is greatly improved.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with a convertible flight attitude.
Background
Unmanned aerial vehicle is abbreviated as "unmanned aerial vehicle", compares with unmanned aerial vehicle, and unmanned aerial vehicle often more is fit for what is too "fooled, dirty or dangerous" task, and unmanned aerial vehicle can divide into for military use and civilian according to application, and unmanned aerial vehicle plus the application of trade is the real just needs of unmanned aerial vehicle, especially an unmanned aerial vehicle that flight gesture is convertible, assists people's better completion task or better experience life.
For example, CN111824402a discloses a unmanned aerial vehicle, which comprises a fuselage and a base. The machine body is provided with a paddle arm, a paddle and an adjusting mechanism, and a first buffer assembly and a second buffer assembly are arranged on the base. According to the invention, the paddle arm is connected with the first connecting arm, the paddle arm stretches and contracts through the horizontal movement of the first connecting arm, and is fixed through the fixing device, so that the telescopic performance of the paddle arm is realized; in addition, the invention also provides a first buffer assembly and a second buffer assembly, wherein the first buffer assembly can play a role in buffering in the vertical direction due to the existence of the first buffer spring when the unmanned aerial vehicle descends; the second buffer assembly can be outwards unfolded when falling, plays an auxiliary buffer role, can ensure the stability of the unmanned aerial vehicle and prevent toppling, and effectively solves the problems in the prior art.
For example, the patent number CN111572761A discloses an unmanned aerial vehicle, which comprises a machine body, a flight cantilever and a propeller blade, wherein an upper-layer oil storage cavity, a middle buffer oil cavity and a lower-layer electric equipment cavity are arranged in the machine body from top to bottom, the upper-layer oil storage cavity and the middle buffer oil cavity are communicated with each other, a flight control board is arranged in the lower-layer electric equipment cavity, a methanol engine is arranged below the propeller blade, and a damping support mechanism is also arranged below the machine body; the invention relates to a flying cantilever, which comprises a flying cantilever, a middle buffer oil cavity, a methanol engine, a flight control board, a cable, an oil pipe channel and a cable channel, wherein the oil pipe channel is used for accommodating an oil pipe, the cable channel is used for accommodating a cable, the side wall of the middle buffer oil cavity is provided with an oil inlet hole connected with one end of the oil pipe, an annular oil storage groove communicated with a plurality of oil inlet holes is arranged in the middle buffer oil cavity, the other end of the oil pipe is connected with the methanol engine, one end of the cable is connected with the flight control board, and the other end of the cable is connected with the methanol engine.
Based on the search of the above two patents and the equipment discovery in the combination prior art, because unmanned aerial vehicle often uses under the abominable circumstances of environment, the environmental condition of electric energy etc. often will not keep up the supply of unmanned aerial vehicle, so can appear unmanned aerial vehicle from the phenomenon of sudden falling in the high altitude, owing to do not take the parachute of installation and play buffer function's constructional device certainly, lead to unmanned aerial vehicle to take place promptly to descend in the high altitude out of control, unmanned aerial vehicle falls down because out of control and heavy, unmanned aerial vehicle's phenomenon of taking place very easily and fall carelessly hits the passer-by, still can not avoid unmanned aerial vehicle to fall down and can break up the main part of organism, can't guarantee to reduce the loss to minimum, and when unmanned aerial vehicle falls to ground, can't cushion the sense of shock of falling when falling down, can't cushion unmanned aerial vehicle't fall the gravity, can't guarantee that unmanned aerial vehicle keeps basic structural integrity after falling down, unmanned aerial vehicle's practicality has still been reduced simultaneously.
Accordingly, in view of the above, research and improvement are performed on the existing structure and the existing defects, and an unmanned aerial vehicle with a convertible flight attitude is provided, so that the purpose of higher practical value is achieved.
Disclosure of Invention
In order to solve the technical problems, the invention provides the unmanned aerial vehicle with the convertible flight posture, which aims to solve the problems that the phenomenon that the unmanned aerial vehicle falls carelessly to hit passers-by easily caused by not installing a parachute and buffering a structural device with a damping effect on the original unmanned aerial vehicle, and the falling gravity of the unmanned aerial vehicle cannot be buffered when the unmanned aerial vehicle falls to the ground, so that the unmanned aerial vehicle cannot be guaranteed to keep basic structural integrity after falling, and the practicability of the unmanned aerial vehicle is reduced.
The purpose and the efficacy of the unmanned aerial vehicle with the convertible flight posture are achieved by the following specific technical means:
an unmanned aerial vehicle with a convertible flight posture comprises a body; the machine body is of a cuboid structure, and a hollow irregular cylinder-shaped ejection box is fixedly arranged at the upper end of the middle of the machine body; the hollow annular buffer cushions are fixedly arranged at the lower middle ends of the ejection boxes respectively; the cushion pads are respectively arranged at four corners of the bottom of the lower end of the middle of the machine body; the machine body comprises wings, vertical rods, solar battens, clamping grooves and converters, a group of wings are respectively installed at four corners of the outer side of the machine body, a group of cylindrical vertical rods are respectively and vertically installed at four corners of the bottom of the lower end of the machine body, the solar battens with strip-shaped grooves are respectively and fixedly installed on the end face of the upper side of the machine body, hollow circular clamping grooves are respectively formed in the upper end of the inner side of the middle of the solar battens, and the converters are respectively and fixedly installed on the right side of the lower end of the clamping grooves.
Further, the ejection box comprises a telescopic column, a fixing rod and a shrinkage opening, wherein the cylindrical telescopic column is fixedly installed on the inner side of the ejection box in the middle, a group of cylindrical fixing rods are vertically installed around the outer side of the telescopic column respectively, and the annular shrinkage opening is installed on the inner side of the fixing rod in the middle.
Further, the blotter includes branch, stand, colludes groove and connector, transversely install a set of cuboid form branch on the blotter outside terminal surface respectively, a set of long banding stand of branch perpendicular lower extreme fixed mounting, stand lower extreme bottom is a set of universal wheel of fixed mounting respectively, and the left and right sides of stand is a set of convex cylinder form collude the groove of fixed mounting respectively, and a set of connector of constituteing by cylinder form and spring on the opposite direction inboard terminal surface of stand respectively.
Furthermore, the bottom of the lower end of the vertical rod on the machine body is fixedly provided with a spherical buckle, and the springs connected with the inner sides of the connectors are respectively connected with the spherical buckle at the bottom of the lower end of the vertical rod.
Further, the shrinkage mouth of ejection case upper end fixed mounting is in the inboard of ejection case upper end fretwork mouth, offers the adjustment tank of a fretwork on the outside terminal surface of ejection case, and the long banding tongue switch of inboard installation in the middle of adjustment tank, and tongue switch up-and-down motion is in the inboard in the middle of fretwork adjustment tank.
Further, the outside of pole setting on the organism encircles two sets of springs of installation respectively, and the cushion collar cover is installed in the outside of centering of pole setting, and two sets of springs press from both sides the blotter each other in the middle with each other about one by one respectively, and the pole setting vertically runs through the inside of centering of two sets of springs of installation and cushion, converter fixed mounting is in the lower extreme bottom of organism, and the solar energy slat of converter and upper end is connected fixed mounting respectively.
Further, a pair of hooking grooves are respectively arranged on the left side and the right side of the supporting rod on the buffer cushion, the hooking grooves at the left side and the right side of the supporting rod are respectively connected with the spring to the hooking grooves at the same side of the upright post, and the spring is used for respectively connecting the hooking grooves at the left side and the right side of the supporting rod with the hooking grooves at the same side of the upright post at the lower end of the supporting rod.
Compared with the prior art, the invention has the following beneficial effects:
because the cylindrical telescopic columns are fixedly arranged on the inner side of the ejection box in the middle, a group of cylindrical fixing rods are vertically arranged around the outer sides of the telescopic columns respectively, the annular shrinkage opening is formed in the connection of the inner sides of the centers of the fixing rods, the shrinkage opening at the upper end of the ejection box is fixedly arranged on the inner side of the hollowed-out opening at the upper end of the ejection box, the inner side of the ejection box is provided with a small parachute device, when an unmanned aerial vehicle falls out of control and emergency, an unmanned aerial vehicle can automatically open the shrinkage opening, the built-in telescopic columns eject out the built-in parachute, and the fixing rods are fixedly arranged above the unmanned aerial vehicle, so that the phenomenon that the unmanned aerial vehicle falls out of control and is carelessly hit a passer can be avoided, the main part of the unmanned aerial vehicle can be broken, the unmanned aerial vehicle device can be timely protected, loss can be guaranteed to be reduced to the minimum, and meanwhile, the safe practical function of the unmanned aerial vehicle is greatly increased;
because transversely install a set of cuboid form branch on the blotter outside terminal surface respectively, a set of long banding stand of branch perpendicular lower extreme fixed mounting, a set of universal wheel of stand lower extreme bottom part fixed mounting respectively, and the left and right sides of stand is the groove of colluding of a set of convex cylinder form of fixed mounting respectively, and a set of connector of constituteing by cylinder form and spring of fixed mounting respectively on the inboard terminal surface of subtend of stand, a pair of groove of colluding is installed respectively to the left and right sides of branch on the blotter, and the groove of colluding of both ends is connected the installation spring respectively to the groove of colluding of stand with one side respectively about the branch, and the spring is with the groove of colluding of both ends about the branch and the groove of colluding of the same one side of stand of lower extreme interconnect respectively, consequently, and collude groove and connector all be the structural device that helps unmanned aerial vehicle to carry out secondary buffering, when unmanned aerial vehicle falls to ground, the key effect has just been played to the part of lower extreme, twice buffering can effectually alleviate the sense of falling, and the universal wheel of lower extreme also can slide a period of time, make the unmanned aerial vehicle more effectively realize that colludes the groove of colludes at three sides and the same sides of stand, the same side of the cushion structure of the unmanned aerial vehicle has increased, the practicality of the unmanned aerial vehicle has guaranteed the full-face structure of falling, the three-down structure of the unmanned aerial vehicle has increased simultaneously, the effect has guaranteed the structure of the unmanned aerial vehicle.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
Fig. 1 is a schematic view of the right front upper shaft structure of the present invention.
Fig. 2 is a schematic view of the right front lower shaft structure of the present invention.
Fig. 3 is an isometric view of a body portion of the present invention.
Fig. 4 is a schematic isometric view of the ejection chamber portion of the present invention.
Fig. 5 is an isometric view of a portion of a cushion of the present invention.
Fig. 6 is an isometric view of a body portion and an ejector box portion of the present invention.
Fig. 7 is an isometric view of the pole portion and cushion portion of the present invention.
In the figure, the correspondence between the component names and the drawing numbers is:
1. a body; 101. a wing; 102. a vertical rod; 103. solar energy laths; 104. a clamping groove; 105. a converter; 2. an ejection box; 201. a telescopic column; 202. a fixed rod; 203. a shrinking opening; 3. a cushion pad; 301. a support rod; 302. a column; 303. a hooking groove; 304. and (5) a connector.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings and examples. The following examples are illustrative of the invention but are not intended to limit the scope of the invention.
In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front," "rear," "head," "tail," and the like are used as an orientation or positional relationship based on that shown in the drawings, merely to facilitate description of the invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "connected," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Examples:
as shown in fig. 1 to 7:
the invention provides an unmanned aerial vehicle with a convertible flight posture, which comprises a machine body 1; the machine body 1 is of a cuboid structure, and a hollow irregular cylinder-shaped ejection box 2 is fixedly arranged at the upper end of the middle of the machine body 1; the middle lower end of the ejection box 2 is fixedly provided with hollow annular buffer cushions 3 respectively; the cushion pads 3 are respectively arranged at four corners of the bottom of the middle lower end of the machine body 1; the machine body 1 comprises wings 101, vertical rods 102, solar ribbon boards 103, clamping grooves 104 and converters 105, a group of wings 101 are respectively installed at four corners of the outer side of the machine body 1, a group of cylindrical vertical rods 102 are respectively and vertically installed at four corners of the bottom of the lower end of the machine body 1, the solar ribbon boards 103 with strip-shaped grooves are respectively and fixedly installed on the end faces of the upper side of the machine body 1, hollow circular clamping grooves 104 are respectively formed in the upper end of the inner side of the middle of the solar ribbon boards 103, converters 105 are respectively and fixedly installed on the right side of the lower end of the clamping grooves 104, the cuboid-shaped structure of the machine body 1 can enable the vertical rods 102 to be firm and durable, the solar ribbon boards 103 are matched with the converters 105 to provide more electric power autonomous supply devices for an unmanned aerial vehicle, the unmanned aerial vehicle can conveniently work in a harsher environment, the practical durability of the unmanned aerial vehicle is improved, the ejection box 2 is further installed to enable the unmanned aerial vehicle to be increased with an emergency device, and the supporting cushion pad 3 can enable the unmanned aerial vehicle to drop down to the ground even when the unmanned aerial vehicle is suddenly stopped.
The ejector box 2 comprises a telescopic column 201, a fixing rod 202 and a shrinkage port 203, the cylindrical telescopic column 201 is fixedly installed on the inner side of the ejector box 2 in the middle, a group of cylindrical fixing rods 202 are vertically installed around the outer side of the telescopic column 201 respectively, the circular shrinkage port 203 is installed on the inner side of the middle of the fixing rods 202 in a connecting mode, the inner side of the ejector box 2 is provided with a small parachute device, when the unmanned aerial vehicle falls in an out-of-control emergency, the shrinkage port 203 is automatically opened by an unmanned aerial vehicle, the built-in telescopic column 201 ejects the built-in parachute, and the fixing rod 202 is fixedly installed above the unmanned aerial vehicle, so that the phenomenon that the unmanned aerial vehicle falls down to the main part of the unmanned aerial vehicle 1 is prevented from being broken by careless falling down is avoided, the unmanned aerial vehicle device is timely protected, loss is guaranteed to be reduced to the minimum, and the safe practical function of the unmanned aerial vehicle is greatly increased.
The cushion pad 3 comprises a supporting rod 301, a vertical column 302, a hooking groove 303 and a connector 304, wherein a group of cuboid supporting rods 301 are transversely arranged on the outer side end face of the cushion pad 3, a group of strip-shaped vertical columns 302 are fixedly arranged at the lower ends of the supporting rods 301, a group of universal wheels are fixedly arranged at the bottoms of the lower ends of the vertical columns 302, a group of convex cylindrical hooking grooves 303 are fixedly arranged at the left side and the right side of the vertical columns 302, a group of connectors 304 consisting of cylindrical bodies and springs are fixedly arranged on the opposite inner side end face of the vertical columns 302, the cushion pad 3 is supported and connected by the supporting rods 301 and the vertical columns 302, the hooking grooves 303 and the connectors 304 are all structural devices for helping the unmanned aerial vehicle to perform secondary buffering, when the unmanned aerial vehicle falls on the ground, the cushion pad 3 at the lower end plays a key role, the impact sense of falling can be effectively relieved through the twice buffering, the universal wheels at the lower end can slide for a period of time, the effect of damping and the same function is improved.
Wherein, the lower extreme bottom fixed mounting ball buckle of pole setting 102 on the organism 1, and the inboard spring of connecting head 304 is connected with the ball buckle of pole setting 102 lower extreme bottom respectively and is installed together, and pole setting 102 and cushion 3 are the constructional device of two parts, but all play unanimous cushioning effect, and the fixed mounting effect of unmanned aerial vehicle structure is played to connector 304, makes unmanned aerial vehicle structure buffer more scientific rationalization.
Wherein, the shrink mouth 203 fixed mounting of ejection case 2 upper end is in the inboard of ejection case 2 upper end fretwork mouth, offer the regulating tank of a fretwork on the outside terminal surface of ejection case 2, the long tongue switch of inboard installation in the middle of regulating tank, and tongue switch up-and-down motion is inboard in the middle of fretwork regulating tank, free switch's shrink mouth 203 can make unmanned aerial vehicle open by oneself under emergency, and install the tongue switch again in the outside for when later stage, make things convenient for people to inspect unmanned aerial vehicle parachute structure maintenance work, unmanned aerial vehicle parachute mechanism's work efficiency has still been improved, unmanned aerial vehicle's practicality has been increased again simultaneously.
The outer sides of the vertical rods 102 on the machine body 1 are respectively and circumferentially provided with two groups of springs, the buffer cushion 3 is annularly arranged on the central outer side of the vertical rods 102, the buffer cushion 3 is respectively clamped in the middle one by the two groups of springs, the vertical rods 102 vertically penetrate through the central inner sides of the two groups of springs and the buffer cushion 3, the converter 105 is fixedly arranged at the bottom of the lower end of the machine body 1, the converter 105 and the solar battens 103 at the upper end are respectively and fixedly arranged, the springs at the upper end and the lower end are fixedly arranged, the shock absorption and buffer functions of the buffer cushion 3 are enhanced, the solar battens 103 are arranged to automatically absorb light energy, the converter 105 is utilized to convert the light energy into kinetic energy, and the unmanned aerial vehicle is used at any time, so that the unmanned aerial vehicle is self-sufficient in energy structure mode, manual charging of manpower is saved, and the same function is improved.
The two sides of the strut 301 on the cushion pad 3 are respectively provided with a pair of hooking grooves 303, the hooking grooves 303 at the left and right ends of the strut 301 are respectively connected with the hooking grooves 303 at the same side of the upright post 302 to be provided with springs, the hooking grooves 303 at the left and right ends of the strut 301 and the hooking grooves 303 at the same side of the upright post 302 at the lower end of the strut are respectively connected with each other by the springs, so that the three hooking grooves 303 are mutually connected to form a triangle-like structural device, the structural support of the strut 301 and the upright post 302 can be effectively assisted to increase stability, the falling gravity of the unmanned aerial vehicle is buffered to the greatest extent, the basic structural integrity is kept after the unmanned aerial vehicle falls down, and the practicability of the unmanned aerial vehicle is increased.
Specific use and action of the embodiment:
when the unmanned aerial vehicle is used, the machine body 1 is of a cuboid structure, the cuboid structure of the machine body 1 can enable the vertical rod 102 to be fixed and support the structure more firmly and durable, the solar ribbon board 103 is matched with the converter 105 to produce more electric power autonomous supply devices for unmanned aerial vehicles, the unmanned aerial vehicles can conveniently work in a harsher environment, the practical durability of the unmanned aerial vehicles is improved, the hollow irregular cylindrical ejection box 2 is fixedly arranged at the upper middle end of the machine body 1, the inner side of the ejection box 2 is provided with a small parachute device, when the unmanned aerial vehicles fall in an emergency way, the shrinkage port 203 is automatically opened by an unmanned aerial vehicle, the built-in telescopic column 201 ejects the built-in parachute out, the solar ribbon board is fixedly arranged above the unmanned aerial vehicles by the fixing rod 202, so that the unmanned aerial vehicles fall down to the main part of the unmanned aerial vehicles can be prevented, the loss is guaranteed to be minimized in time, the buffer pad 3 is respectively arranged at four corners at the bottom of the middle lower end of the machine body 1, the buffer pad 3 is connected by the support rod 301 and the vertical column 302, and the buffer pad 3 is a buffer pad is further effectively and the buffer 3 is lowered down to the ground, and the buffer 3 is more effective and the buffer device is lowered down for the two time is realized;
in addition, the bottom of the lower end of the vertical rod 102 on the machine body 1 is fixedly provided with a round ball buckle, springs connected with the inner side of a connector 304 are respectively connected with the round ball buckle at the bottom of the lower end of the vertical rod 102, the vertical rod 102 and the buffer pad 3 are two-part structural devices, but play a role in uniform buffer, the connector 304 plays a role in fixedly installing an unmanned plane structure, the outer side of the vertical rod 102 on the machine body 1 is respectively provided with two groups of springs in a surrounding manner, the buffer pad 3 is sleeved on the central outer side of the vertical rod 102, the two groups of springs clamp the buffer pad 3 in the middle one by one, the vertical rod 102 vertically penetrates through the central inner side of the two groups of springs and the buffer pad 3, the converter 105 is fixedly arranged at the bottom of the lower end of the machine body 1, the converter 105 and the solar ribbon board 103 at the upper end are respectively connected and fixedly arranged, thus the springs at the upper end and the lower end are connected with the buffer pad 3 for fixedly mounting, the shock absorption and buffering functions of the cushion pad 3 are enhanced, the solar ribbon board 103 is arranged to automatically absorb light energy, the converter 105 is utilized to convert the light energy into kinetic energy, the unmanned aerial vehicle is used at any time, thus the unmanned aerial vehicle is self-sufficient in energy structure mode, manual charging of manpower is saved, the shrinkage port 203 at the upper end of the ejection box 2 is fixedly arranged at the inner side of the hollowed-out port at the upper end of the ejection box 2, the outer end surface of the ejection box 2 is provided with a hollowed-out regulating groove, the middle inner side of the regulating groove is provided with a strip-shaped convex groove switch, the convex groove switch moves up and down at the middle inner side of the hollowed-out regulating groove, the shrinkage port 203 of the free switch can enable the unmanned aerial vehicle to be automatically opened under emergency, and the outer part is provided with the convex groove switch, so that people can conveniently inspect and maintain the parachute structure of the unmanned aerial vehicle in later period, the working efficiency of unmanned aerial vehicle parachute mechanism has still been improved, the left and right sides of branch 301 on the blotter 3 respectively installs a pair of groove 303 that colludes, and the groove 303 that colludes of both ends about branch 301 connects the installation spring respectively to the groove 303 that colludes of stand 302 homonymy respectively, and the groove 303 that colludes of the same side of stand 302 of both ends and lower extreme interconnect about the spring will branch 301, three department colludes groove 303 interconnect and constitutes like triangle body form constructional device like this, can effectually help branch 301 and stand 302's structural support increase steadiness, carry out furthest's buffering unmanned aerial vehicle's gravity that falls.
The embodiments of the invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (6)
1. An unmanned aerial vehicle with convertible flight posture, which is characterized in that: comprises a machine body (1); the machine body (1) is of a cuboid structure, and a hollow irregular cylindrical ejection box (2) is fixedly arranged at the upper end of the middle of the machine body (1); the hollow annular buffer cushions (3) are fixedly arranged at the lower ends of the centers of the ejection boxes (2) respectively; the cushion pads (3) are respectively arranged at four corners of the bottom of the middle lower end of the machine body (1); the machine body (1) comprises wings (101), vertical rods (102), solar battens (103), clamping grooves (104) and converters (105), a group of wings (101) are respectively arranged at four corners on the outer side of the machine body (1), a group of cylindrical vertical rods (102) are respectively and vertically arranged at four corners on the bottom of the lower end of the machine body (1), solar battens (103) with strip-shaped grooves are respectively and fixedly arranged on the upper end face of the upper side of the machine body (1), hollow circular clamping grooves (104) are respectively arranged at the upper ends of the inner sides of the centers of the solar battens (103), and the converters (105) are respectively and fixedly arranged on the right sides of the lower ends of the clamping grooves (104);
the buffer pad (3) comprises a supporting rod (301), a vertical column (302), a hooking groove (303) and a connector (304), a group of cuboid supporting rods (301) are transversely arranged on the outer side end face of the buffer pad (3), a group of long-strip-shaped vertical columns (302) are fixedly arranged at the vertical lower ends of the supporting rods (301), a group of universal wheels are fixedly arranged at the bottoms of the lower ends of the vertical columns (302), a group of convex cylindrical hooking grooves (303) are fixedly arranged at the left side and the right side of the vertical columns (302), and a group of connectors (304) consisting of cylindrical springs are fixedly arranged on the opposite inner side end faces of the vertical columns (302).
2. The convertible-flight unmanned aerial vehicle of claim 1, wherein: the ejection box (2) comprises a telescopic column (201), a fixing rod (202) and a shrinkage port (203), wherein the cylindrical telescopic column (201) is fixedly installed on the inner side of the ejection box (2) in the middle, a group of cylindrical fixing rods (202) are vertically installed around the outer side of the telescopic column (201) respectively, and the circular shrinkage port (203) is installed on the inner side of the fixing rod (202) in the middle in a connecting mode.
3. The convertible-flight unmanned aerial vehicle of claim 1, wherein: the bottom of the lower end of the vertical rod (102) on the machine body (1) is fixedly provided with a spherical buckle, and springs connected with the inner side of the connector (304) are respectively connected with the spherical buckle at the bottom of the lower end of the vertical rod (102).
4. The convertible-flight unmanned aerial vehicle of claim 1, wherein: the shrinkage mouth (203) fixed mounting of launch case (2) upper end is in the inboard of launch case (2) upper end fretwork mouth, sets up the regulating groove of a fretwork on launch case (2) the outside terminal surface, and the long banding tongue switch of inboard installation placed in the middle of regulating groove, and tongue switch up-and-down motion is in the inboard placed in the middle of fretwork regulating groove.
5. The convertible-flight unmanned aerial vehicle of claim 1, wherein: the outside of pole setting (102) on organism (1) encircles respectively and installs two sets of springs, and blotter (3) ring cover is installed in the outside of centering of pole setting (102), and two sets of springs press from both sides blotter (3) each other in the middle respectively one by one, and pole setting (102) vertically run through the inside of centering of installing two sets of springs and buffer pad (3), converter (105) fixed mounting is in the lower extreme bottom of organism (1), and solar energy slat (103) of converter (105) and upper end connect fixed mounting respectively.
6. The convertible-flight unmanned aerial vehicle of claim 1, wherein: the left side and the right side of the supporting rod (301) on the cushion pad (3) are respectively provided with a pair of hooking grooves (303), the hooking grooves (303) at the left end and the right end of the supporting rod (301) are respectively connected with the hooking grooves (303) at the same side of the upright post (302) to be provided with springs, and the springs are respectively connected with the hooking grooves (303) at the left end and the right end of the supporting rod (301) and the hooking grooves (303) at the same side of the upright post (302) at the lower end of the supporting rod.
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| CN202110022100.4A CN112678192B (en) | 2021-01-08 | 2021-01-08 | Unmanned aerial vehicle with convertible flight posture |
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| CN202110022100.4A CN112678192B (en) | 2021-01-08 | 2021-01-08 | Unmanned aerial vehicle with convertible flight posture |
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| CN112678192B true CN112678192B (en) | 2023-08-25 |
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